WO2002083498A1 - Microwave device for de-icing or keeping the surface of dimensionally stable hollow body structures free from ice and method for the operation of said device - Google Patents
Microwave device for de-icing or keeping the surface of dimensionally stable hollow body structures free from ice and method for the operation of said device Download PDFInfo
- Publication number
- WO2002083498A1 WO2002083498A1 PCT/EP2002/002842 EP0202842W WO02083498A1 WO 2002083498 A1 WO2002083498 A1 WO 2002083498A1 EP 0202842 W EP0202842 W EP 0202842W WO 02083498 A1 WO02083498 A1 WO 02083498A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- microwave
- edge
- hollow body
- ice
- area
- Prior art date
Links
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B6/00—Heating by electric, magnetic or electromagnetic fields
- H05B6/64—Heating using microwaves
- H05B6/80—Apparatus for specific applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/06—Liquid application
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
- B64D15/14—De-icing or preventing icing on exterior surfaces of aircraft by electric heating controlled cyclically along length of surface
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
- F03D80/40—Ice detection; De-icing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63J—AUXILIARIES ON VESSELS
- B63J2/00—Arrangements of ventilation, heating, cooling, or air-conditioning
- B63J2/12—Heating; Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
- H05B2214/02—Heaters specially designed for de-icing or protection against icing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- Microwave device for keeping ice free and defrosting dimensionally stable hollow body structures on the surface and method for operating the device
- the invention relates to a microwave technology device for keeping ice free and defrosting dimensionally stable hollow body structures on the surface which are exposed to meteorological influences and are kept ice-free at least in sections in the surface area of the edges against which atmospheric air flows.
- the cavity / shell structures consist of composite materials hardened with thermoplastic or thermosetting plastic systems with dielectric properties.
- the system has at least one microwave source, the output of which can be controlled, pulsed or operated continuously, via a flanged waveguide and decoupling system in the frequency range from 900 MHz to 20 GHz and emits monochromatic signals.
- At least the front of the respective structure, which is at risk of icing has a laminated structure, which consists of a molded body as a support structure made of dielectric composite material with a shear, pressure and bending strength adapted to the stress.
- the structure is externally covered with a metallic skin as lightning protection.
- a metallic skin In connection with other adjoining or directly adjacent building structures with a metallic surface, it is connected in an electrically conductive manner, so that there is also a metal-enclosed cavity.
- At least one microwave system that is operated on its own is installed in the cavity or in chambers of each such shaped body and consists of a microwave source with a power supply unit and decoupling device comprising a waveguide and decoupling structure.
- the outcoupling structure is set up in the interior of the molded body along the outer inflow front in such a way that the outcoupled microwave impinges on the inside along it with a wavefront or almost with a wavefront on the free inner surface of the composite material.
- the metal skin is thus kept at a predeterminable temperature, corresponding to the meteorological requirements, from the melting point of 0 ° C to + 70 ° C and defrosting speed, at which there is certainly no ice formation on the air-flowed front when the microwave system is switched on, or there is ice on the inflow front the contact surface is thawed / defrosted when the microwave system is switched on.
- the object of the invention is to provide a structurally simple, compact, decentralized deicing device for hollow or shell body structures which are exposed to an atmospheric air flow.
- the object is achieved by microwave de-icing device according to the preamble of claim 1 and its characterizing features and a method for operating the device according to claim 7.
- the area of the hollow body structure exposed to the atmosphere is to be de-iced in sections or partially along an edge against which the air flow flows or to be kept free of ice.
- This area, to be kept free of ice or to be de-iced is divided along the edge into lined up surface segments.
- Each of these segments has two boundaries running away from the edge, each of which coincides with the line of abutment on the wall of the hollow body of a rib anchored there in the hollow body.
- the boundary line of the respective surface segment closes completely along two lines, which coincide with the two butt lines on the hollow body wall of a spar anchored in the hollow body structure.
- the waveguide decoupling structure is attached to the inside of the spar wall as seen from it, parallel to the edge. It is flanged through the wall of the spar to its associated microwave source.
- the geometry of the chambers and the frequency of the microwave is such that an electromagnetic field with overmodulation, that is to say the occurrence of many possible modes, is excited in each chamber with the associated microwave source switched on.
- the microwave penetrates into the wall of fiber composite material, CFRP or GFRP, of the surface segment and heats up with the same or almost the same power surface density this according to the electrical properties, i.e. the electrical conductivity. Due to the metal skin shielding the respective surface segment on the outside, the microwave cannot step outside.
- the entire chamber is microwave-tight to the outside.
- metallic double lines made of electrically highly conductive material are embedded in the wall of the hollow body structure. These line double lines are completely closed by hoses with the microwave sources or with their respective cooling channel to form a coolant circuit in such a way that there is always a counterflow in the double lines and the microwave sources are flowed through in succession. With stationary operation of the microwave sources, there is therefore a same temperature along the double lines with an appropriate design, which results solely from the waste heat of the microwaves.
- Each coolant circuit can be connected to another heat source for safety, but that would be a common measure that would be taken if redundancy had to be set up for such a system.
- the method of operating a microwave de-icing device is also part of the invention.
- One process is the continuous ice-free keeping of the linear structure in the area on the exposed, exposed surface of the cavity structure by means of the double lines laid in the wall.
- counterflow is obtained in the double line area, ie the flow in both lines is opposite there, and a fluidic connection in series the heat sources, the microwave sources from the area through which coolant is pumped.
- the microwave sources of an area are operated cyclically. That at least one microwave is switched on for an adjustable time, the others are not and vice versa. There is always one switched off between two switched on microwave sources. Depending on the number of microwave sources, the cycle time is due to the necessary on and off times for each microwave source.
- This single cycle time of an area can be coupled with that of other areas to a higher cycle time by adding the individual cycle times, that would be a sequential operation, or by operating the areas independently of each other, that would be a kind of simultaneous operation.
- simultaneous operation in groups can also be set up. But this is a tax issue and is based on the heat requirement.
- At least one microwave source from such a region is always switched on and generates waste heat for line heating.
- the close vicinity of the double lines is constantly warm during a cycle time via the variable efficiency of the microwave sources, and due to the dimension of the microwave de-icing device it is so warm that the line structure remains ice-free and any ice layer present on a surface segment from this area of the hollow body.
- Structure is thawed in its boundary layer to the hollow body during the associated switched-on microwave source and is prematurely torn off from the surface or just thawed further with a sufficiently strong air flow.
- the intermediate line areas can therefore build up ice for a short time. Therefore the always ice-free Li Areas of such an area are also dimensioned such that the surfaces in between can always be made ice-free quickly and safely using a microwave.
- the microwave sources can be operated in a continuous wave during their respective switch-on times or with a lower heat requirement in accordance with pulse width control.
- operation which is appropriate to the heat requirement can always be set in a technically simple manner known from other technical fields and can be controlled / adaptively carried out with the aid of temperature and icing sensors and data processing devices.
- the waveguide-like coupling structure over the length of the chamber has a round cross section (claim 2).
- the rectangular cross section thereof is described, with which the overmodedness, i. H. the appearance of many possible modes, starting with the basic mode in the chamber is stimulated.
- the sources listed in claim 4 come as microwave sources, such as the magnetron, the klystron, the backward wave oscillator (BWO), or the extended interaction oscillator, from the English Extended Interaction Oscillator, EIO, even also the gyrotron and finally Klystroden, in question.
- BWO backward wave oscillator
- EIO English Extended Interaction Oscillator
- Klystroden the English Extended Interaction Oscillator
- the weight of the microwave source is often a factor that cannot be overlooked.
- the pipes are made of a material that conducts the heat well, such as copper or brass or stainless steel.
- the cross section of these lines can be round or polygonal (claim 5). The selection will be based on the installation and manufacture of the hollow body structure. A technically obvious cross-section is round, but a polygonal one, such as triangular, square or hexagonal, is common.
- the design of the microwave technology device is based on the fact that sufficient microwave power is available for the rapid thawing of an ice layer.
- microwave sources are also used that can meet this requirement. With an efficiency between 0.4 and 0.8 in the best case, the source in any case produces heat, which is absorbed here by the coolant flowing past in the cooling coil of the source and transported to the linear use location.
- a coolant circuit therefore consists at least of the double lines and associated microwave sources of an area to be kept free of ice and to be de-iced (claim 6). The waste heat from the microwave sources is used in a targeted manner and is not released into the environment unused. If the coolant circuit does not start to move solely due to the temperature gradient in the circuit, an actively operated coolant pump is installed in the circuit, at least for the start (claim 7). Once it has started and is sufficiently strong, the pump can continue to run passively.
- the coolant circuit with the heat / microwave sources connected in series with one another is connected to another heat source via valves. But this is a measure that is technically known and is taken if necessary.
- the microwave power emerges at the decoupling device with low attenuation and heats the shell structure exposed to the atmosphere, which acts as a dissipative resonator of very low quality, sectionally evenly in sections with a predetermined time cycle and continuously along a predetermined line area with the waste heat of the microwave sources used in the area.
- the microwave de-icing device can be easily installed on site in such hollow body structures, so that the microwave engineering construction work remains limited to the microwave source, the decoupling structure and, if need be, a short connecting piece from the source to the decoupling structure.
- the power supply unit for groups of microwave sources, the groups must be kept free of ice for an area to be de-iced, is located centrally. Only high-voltage supply lines go from it to the microwave sources.
- a coolant circuit has at least one group of microwave sources connected in series in terms of flow technology, better their respective cooling coils than heat sources. at In several groups, the cooling circuit is driven by a centrally located pump.
- Such hollow body structures can be devices / structures of a ship or a train or a means of transport to be kept free of ice or the rotor blades of a wind power plant or other structures that can be dealt with under all meteorological conditions.
- the microwave de-icing device can be used in many technical devices that are in any way exposed to the atmosphere. In addition to use on land and on water, its importance in aviation for aviation safety should be emphasized.
- FIG. 1 the elevator and vertical tail in perspective with the indicated installation of the microwave technology device in the horizontal tail
- FIG. 2 shows the horizontal stabilizer with the built-in microwave technology device
- FIG. 3 shows the areas on the heights and vertical tail to be kept free of ice
- FIG. 4 shows the fluidic connection.
- Sources with sufficient microwave power can be considered as microwave sources, which can excite such a multimodal or overmodel electromagnetic field via the decoupling structure in the chamber that the electromagnetic wave penetrating into the wall of the surface segment produces a qualified Alternatively, there is surface-uniform / homogeneous heating that thaws the boundary layer between the surface segments and the ice layer in all expected weather conditions and temperatures.
- the microwave power to be emitted is determined from these specifications, the electrical property - conductance - the hollow body wall and the necessary multimodality in the respective chamber, and the source is then selected. Since an ample selection can be made here, the frequency range from about 900 MHz to about 25 GHz, in which the selected source must work, should be mentioned here.
- the wall of the elevator and vertical tail is made of a fiber composite, at least in the areas to be de-iced.
- CFRP carbon fiber composites
- These have a certain electrical conductivity, so the penetrating microwave couples. In the case of other fiber composite materials, this can be adjusted if necessary by adding additives in the manufacture of semi-finished products.
- the cooling device of the heat source works in a similar way to the device for producing hot water in a coffee machine: the cold liquid medium is heated and driven forward. If the heating is sufficiently powerful, then a naturally driven cycle is created if the friction is not too high.
- FIG. 1 shows the horizontal tail and the intersection with the vertical tail.
- the horizontal stabilizer indicates the structure of the microwave technology device, but not in the vertical stabilizer, although, also provided there, as later on from FIG. 3 evident.
- the two areas on the horizontal stabilizer, which are arranged in mirror-image relation to one another with respect to the vertical stabilizer, are highlighted here. Each area is divided into four surface areas. This is indicated by the four tubular decoupling structures which are lined up next to one another and which, seen from the vertical tail, have each flanged the associated microwave source at their beginning.
- the microwave source used here is, for example, as described in relation to FIG.
- a magnetron the microwave power output of which is required by the heat requirement, better the heat requirement power of the wall of the assigned surface segment for sufficiently rapid heating of the metal skin there.
- the waste heat of the magnetron is determined from its efficiency, which is between about 0.4 and 0.8 depending on that.
- the power supply unit supplying the microwaves / magnetrons is accordingly dimensioned at least for the most powerful cycle.
- Figure 2 shows the situation on one wing half of the horizontal stabilizer more clearly.
- the vertical tail is no longer indicated, it has been removed and shows the power supply between the two wings for supplying the two areas in the horizontal tail and the area not indicated here in the vertical tail (see FIG. 3).
- Four semiconductor-shaped decoupling devices are mounted one behind the other along the leading edge of the wing at a predetermined distance from the latter and the wing wall there on the spar running there.
- the thick double lines indicate the course of the double lines in the wing wall and at the same time, with their two-sided branches from the leading edge to the rear, indicate the surface areas of the area to be de-iced that are of the same area.
- the environment along the lines is heated by the cooling circuit in such a way that it is constantly ice-free.
- the ribs in the wing also run to the rear and form the respective chamber together with the spar part wall and the wing segment wall their decoupling device.
- the five double lines dip into the inside of the wing on both sides and couple via hoses to the cooling screw of the respective microwave source, in such a way that the heat sources lie one behind the other in the cooling circuit and the coolant flow in the double line branches and along the leading edge are opposite , A principle of conduction is clearly shown in FIG. 4.
- FIG. 3 the situation of three ice-free line areas and the associated, to be made ice-free, equal surface segments on the elevator and vertical tail are shown schematically.
- the two horizontal stabilizer areas are mirror images of one another and, in contrast to FIGS. 1 and 2, are each divided into only three identical surface segments 1, 2 and 3 by the outgoing double line branches.
- the simple surface segment 4 lying vertically underneath is that of the vertical tail.
- the respectively delimiting two thin lines of the areas indicate the trace of the spar belonging to the area.
- the thick solid lines show the subdivision and thus indicate the routing of the pipes of the respective cooling circuit.
- the crossed thick line runs along the leading edge, in the vertical tail this is limited at the top and bottom. The dimensions are provided here as an example for a passenger aircraft of a smaller design.
- the thick lines over the pipes of the cooling circuit device laid in the wing wall select a cyclical operating mode in such a way that the two areas 1 with their areas on both sides of the leading edge on the vertical guide factory, ie the four areas assigned to it are heated using a microwave, for example for 30 seconds, then cycle areas 2, 3 and finally cycle area 4 on the vertical tail, in order to then start again with the following cycle at 1.
- the area cycle is therefore 1, 2, 3, 4. If the two cycle areas 1 are heated, the others here are not heated during this time.
- the cycle time means that only the two microwave sources for the surface segments are 1 2 heat sources, then 2, 3 and finally 4. Then the cycle starts again at 1.
- FIG. 4 shows a coolant circuit which contains at least one group of double lines and the associated microwave sources or their heat sources.
- the illustration is shown schematically in the plane. It shows the continuous double line area along the inflow edge and the double line branches leaving perpendicularly on both sides thereof.
- the double line branches on one side are extended and have the microwave sources at the end.
- the coolant pump is built into the circuit as an example and here for the sake of clarity. Due to this arrangement and connection method, the microwave sources are connected in series as required in terms of flow technology and the double lines have a return flow.
- the double line branches each of which leads to a microwave source, plunge into the hollow body structure.
- There are two temperature differences that contribute to driving the coolant circuit firstly ⁇ T MQ at the cooling coil of the microwave source and secondly ⁇ T H w on the way from the hollow body wall to the microwave source.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE50202322T DE50202322D1 (en) | 2001-04-11 | 2002-03-14 | MICROWAVE TECHNICAL DEVICE AND METHOD FOR IRRITATION OF HOLLOW BODY STRUCTURES |
EP02724233A EP1377503B1 (en) | 2001-04-11 | 2002-03-14 | Microwave device for de-icing or keeping the surface of dimensionally stable hollow body structures free from ice and method for the operation of said device |
AT02724233T ATE289562T1 (en) | 2001-04-11 | 2002-03-14 | MICROWAVE TECHNICAL DEVICE AND METHOD FOR KEEPING HOLLOW BODY STRUCTURES FREE OF ICE |
US10/684,130 US6787744B1 (en) | 2001-04-11 | 2003-10-10 | Microwave device for de-icing, or keeping hollow bodies free from ice and method for the operation of the device |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10118121A DE10118121A1 (en) | 2001-04-11 | 2001-04-11 | Microwave device for preventing ice formation on and deicing surfaces of dimensionally stable hollow body structures for use in aeronautics to keep wing leading edges free of ice |
DE10118121.3 | 2001-04-11 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/684,130 Continuation-In-Part US6787744B1 (en) | 2001-04-11 | 2003-10-10 | Microwave device for de-icing, or keeping hollow bodies free from ice and method for the operation of the device |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002083498A1 true WO2002083498A1 (en) | 2002-10-24 |
Family
ID=7681254
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2002/002842 WO2002083498A1 (en) | 2001-04-11 | 2002-03-14 | Microwave device for de-icing or keeping the surface of dimensionally stable hollow body structures free from ice and method for the operation of said device |
Country Status (6)
Country | Link |
---|---|
US (1) | US6787744B1 (en) |
EP (1) | EP1377503B1 (en) |
AT (1) | ATE289562T1 (en) |
DE (2) | DE10118121A1 (en) |
ES (1) | ES2233815T3 (en) |
WO (1) | WO2002083498A1 (en) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7124983B2 (en) * | 2004-08-20 | 2006-10-24 | Honeywell International, Inc. | Hybrid electrical ice protection system and method including an energy saving mode |
GB2417937B (en) * | 2004-09-10 | 2009-08-12 | Ultra Electronics Ltd | An aircraft wing coupling arrangement |
US20090241509A1 (en) * | 2008-03-25 | 2009-10-01 | Isaac Jon Hogate | Turbine engine inlet strut deicing |
GB0917879D0 (en) * | 2009-10-13 | 2009-11-25 | Airbus Uk Ltd | Aircraft fuel system |
US8505273B2 (en) * | 2009-11-03 | 2013-08-13 | General Electric Company | System for ice and/or frost prevention using guided wave energy |
US9056684B2 (en) * | 2011-04-08 | 2015-06-16 | Textron Innovations Inc. | Rotor blade de-icing system |
US10579080B2 (en) * | 2018-04-06 | 2020-03-03 | Simmonds Precision Products, Inc. | Intelligent ice protection network |
CN109050938B (en) * | 2018-08-14 | 2022-02-08 | 中国电子科技集团公司第三十八研究所 | Microwave deicing device for airplane |
CN110725779B (en) * | 2019-11-01 | 2022-10-25 | 新疆金风科技股份有限公司 | Air cooling system, wind generating set and cooling method thereof |
US11421547B2 (en) | 2020-01-06 | 2022-08-23 | Rohr, Inc. | Thermal-anti-icing system with microwave system |
US20230002064A1 (en) * | 2021-06-30 | 2023-01-05 | Rohr, Inc. | Integrated microwave thermal anti-icing system |
CN113931812A (en) * | 2021-10-28 | 2022-01-14 | 浙江大学包头工业技术研究院 | Wind driven generator blade deicing device capable of realizing automatic temperature control |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5615849A (en) * | 1995-04-14 | 1997-04-01 | Salisbury; Jonathan T. | Microwave deicing and anti-icing system for aircraft |
WO1998001340A1 (en) * | 1996-07-03 | 1998-01-15 | Lm Glasfiber A/S | A method and a system for deicing of airfoil wings of composite material |
DE19750198A1 (en) * | 1997-11-13 | 1999-05-27 | Karlsruhe Forschzent | High efficiency microwave de- and anti-icing system for aircraft |
DE10016261A1 (en) | 2000-04-03 | 2001-10-18 | Karlsruhe Forschzent | Compact microwave system for de-icing and / or preventing icing of the outer surface of cavity or shell structures exposed to meteorological influences |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4060212A (en) * | 1976-04-01 | 1977-11-29 | System Development Corporation | Deicing apparatus and method |
US5061836A (en) * | 1990-01-18 | 1991-10-29 | United Technologies Corporation | Microwave deicing for aircraft engine propulsor blades |
DE10016259C2 (en) * | 2000-04-03 | 2002-06-20 | Karlsruhe Forschzent | Compact millimeter wave device for defrosting and / or preventing icing |
-
2001
- 2001-04-11 DE DE10118121A patent/DE10118121A1/en not_active Ceased
-
2002
- 2002-03-14 ES ES02724233T patent/ES2233815T3/en not_active Expired - Lifetime
- 2002-03-14 WO PCT/EP2002/002842 patent/WO2002083498A1/en not_active Application Discontinuation
- 2002-03-14 EP EP02724233A patent/EP1377503B1/en not_active Expired - Lifetime
- 2002-03-14 DE DE50202322T patent/DE50202322D1/en not_active Expired - Lifetime
- 2002-03-14 AT AT02724233T patent/ATE289562T1/en not_active IP Right Cessation
-
2003
- 2003-10-10 US US10/684,130 patent/US6787744B1/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5615849A (en) * | 1995-04-14 | 1997-04-01 | Salisbury; Jonathan T. | Microwave deicing and anti-icing system for aircraft |
WO1998001340A1 (en) * | 1996-07-03 | 1998-01-15 | Lm Glasfiber A/S | A method and a system for deicing of airfoil wings of composite material |
DE19750198A1 (en) * | 1997-11-13 | 1999-05-27 | Karlsruhe Forschzent | High efficiency microwave de- and anti-icing system for aircraft |
DE10016261A1 (en) | 2000-04-03 | 2001-10-18 | Karlsruhe Forschzent | Compact microwave system for de-icing and / or preventing icing of the outer surface of cavity or shell structures exposed to meteorological influences |
Also Published As
Publication number | Publication date |
---|---|
US20040173605A1 (en) | 2004-09-09 |
ES2233815T3 (en) | 2005-06-16 |
EP1377503A1 (en) | 2004-01-07 |
DE50202322D1 (en) | 2005-03-31 |
ATE289562T1 (en) | 2005-03-15 |
DE10118121A1 (en) | 2002-10-24 |
US6787744B1 (en) | 2004-09-07 |
EP1377503B1 (en) | 2005-02-23 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1268274B1 (en) | Compact microwave system for deicing and/or preventing icing of the outer surface of hollow or shell structures subject to meteorological influences | |
EP1284903B1 (en) | Compact millimeter wave technical system for de-icing and/or preventing the formation of ice on the outer surface of hollow or shell structures exposed to meteorological influences | |
WO2002083498A1 (en) | Microwave device for de-icing or keeping the surface of dimensionally stable hollow body structures free from ice and method for the operation of said device | |
DE69818992T2 (en) | DEVICE AND METHOD FOR HEATING AND DEFROSTING WIND TURBINE BLADES | |
DE2713080A1 (en) | DEFROSTING DEVICE AND METHOD | |
DE102011119844A1 (en) | Composite structure with ice protection device and manufacturing process | |
DE19750198C2 (en) | Aircraft de-icing with microwaves | |
DE102007026246B4 (en) | Component for an aircraft | |
EP2926984B1 (en) | Method for repairing an electric heating element of a wind turbine rotor blade | |
DE102015013369A1 (en) | Heated aerodynamic attachments | |
WO2010105744A2 (en) | Cooler for an aircraft cooling system, aircraft cooling system and method for operating an aircraft cooling system | |
EP2281748A1 (en) | Device for deicing airplanes | |
EP1438727A1 (en) | Heating film consisting of a plurality of layers and method for producing the same | |
EP3020638A1 (en) | Device and method for de-icing and/or avoiding ice-buildup and profiled body and aircraft equipped with such a device | |
DE102008060572A1 (en) | Apparatus for heating plastic containers and resonator therefor | |
WO2016150592A1 (en) | Air gap-insulated muffler | |
DE102016203496A1 (en) | Electric heater with PTC element and electrical supply lines as Wärmeleitkörper and operating fluid tank with such a heater | |
DE4210885C2 (en) | Heater | |
DE1476989A1 (en) | Device for defrosting the evaporator of a refrigeration machine | |
EP3560844B1 (en) | Packaging machine with heated grid | |
DE102009061028B4 (en) | An aircraft cooling system and method for operating an aircraft cooling system | |
DE202012101314U1 (en) | Heating device for an outer lining of a vehicle | |
DE1936061A1 (en) | De-icing device for aircraft | |
DE102022115054A1 (en) | wing body | |
WO2017032803A1 (en) | Heating system for electrothermal temperature control, and method for the production thereof |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ PL PT RO RU SD SE SG SI SK SL TJ TM TR TT TZ UA UG US UZ VN YU ZA ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2002724233 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 10684130 Country of ref document: US |
|
WWP | Wipo information: published in national office |
Ref document number: 2002724233 Country of ref document: EP |
|
REG | Reference to national code |
Ref country code: DE Ref legal event code: 8642 |
|
WWG | Wipo information: grant in national office |
Ref document number: 2002724233 Country of ref document: EP |
|
NENP | Non-entry into the national phase |
Ref country code: JP |
|
WWW | Wipo information: withdrawn in national office |
Country of ref document: JP |